SHASHI BHUSHAN VERMA DR

Dr. Verma’s research interests are in the study of flow separation in subsonic, transonic and supersonic regimes and in developing appropriate flow control technologies to alleviate their adverse effects. In particular, the focus areas include flow separation associated side-load development in liquid rocket engine nozzles before launch vehicle lift-off, shock-induced supersonic and transonic Interactions related to air-intakes and, afterbody flows and freestream-jet interactions related to projectiles and powered missiles. His experimental efforts focus predominantly on the development of flow control strategies such as side-load reduction designs (e.g., altitude adaptive nozzle concepts or implementing modifications on the launch pad) for high performance rocket engines, innovative steady micro-jet configurations and low-profile mechanical vortex-generating devices for separation control in various shock-wave boundary-layer interactions and, thrust vector control techniques for stealth aircraft applications.

He has co-edited, with Prof. Abdellah Hadjadj of University of Rouen, a special issue in Shock Waves Journal on `Supersonic Control'. Presently his high-speed group is actively working on `Smart Strategies on Flow Separation Control Management’ funded by Aeronautical Research and Development Board (AR&DB), India. He is also involved in joint collaborations with the Nozzle Flow Group at DLR Lampoldshausen Germany, CFD group – INSA de Rouen, France, Space propulsion and Institute for Aerodynamics and Fluid Mechanics at Technical University Munich, Nozzle Test Facility group at Vikram Sarabhai Space Centre, Trivandrum and Aerospace departments of MIT Chennai and DIAT Pune.

Research Interest(s)

Development of innovative flow separation control devices for subsonic, transonic and supersonic interactions.